论文部分内容阅读
针对2种扩张流道的RBCC燃烧室构型,通过三维数值模拟和地面直连试验,研究了燃烧室结构参数以及火焰稳定装置等对亚燃模态性能的影响。结果表明,第二级燃烧室采用较小的扩张角,有利于燃料的进一步燃烧,减小总压损失,燃料支板和凹腔火焰稳定器的共同使用,能有效提升燃烧室内的燃烧组织效果,扩展火焰的传播范围;直连试验验证了通过构型的改进,燃烧室性能得到大幅提高,压力积分推力增大了682 N。当凹腔距离燃料支板较近时,火箭关闭之后,燃料能够实现自持燃烧,比冲性能可提高50%。通过减小主支板宽度,在来流Ma=4时,能够更容易在隔离段中建立预燃激波系,保证亚燃燃烧反应更好地进行,燃烧室内推力提高了418 N。
According to the configuration of RBCC combustion chamber with two kinds of expansion flow channels, the influence of combustion chamber structure parameters and flame stabilizing device on the properties of the sub-combustion mode was studied by three-dimensional numerical simulation and ground direct connection test. The results show that the second stage combustion chamber with a smaller expansion angle is conducive to further fuel combustion, reducing the total pressure loss, the fuel support plate and the cavity flame stabilizer together, can effectively improve the combustion chamber combustion organization , Extending the propagation range of the flame. The direct connection test verified that the combustion chamber performance was greatly improved and the pressure integral thrust increased by 682 N through the improvement of the configuration. When the cavity is closer to the fuel plate, the fuel can achieve self-sustaining combustion with the rocket closed and the specific impulse performance can be increased by 50%. By reducing the width of the main struts, it is easier to establish a pre-fired system in the isolation section at Ma = 4 to ensure that the sub-combustion reaction proceeds better and the thrust in the combustion chamber increases by 418 N.